Aircraft



Sept. 25, 1945 H. L BOWERS AIRCRAFT 3 Sheets-Shet 1 Filed Aug. 13, 1942 \NVENTOR Hanan L. Ibowuxs Sept. 25, 1945. H. L. owERs 2,385,493

' AIRCRAFT I Filed Aug. 13, 1942 3 Sheets-Sheet 2 INVENTOR Hangar Lbowuxs S p 1945- I H. L. BOWE'QRS 2,385,493

AIRCRAFT Filed Aug. 13, 1942 5 Sheets-Sheet 3 INVENTOR Hearsay L. Bowen Patented Sept. 25, 1945 i I STATES PATENT OFFICE AIRCRAFT Herbert L. Bowers, Kenmore, N. Y., assignor to Bell Aircraft Corporation, Buffalo, N. Y.

Application August 13, 1942, Serial No. 454,629 12 Claims. (01. 244-121) I This invention relates to aircraft, and more its rear end by me of a Stationary py particularly to improvements in sliding and deor fuselage deck back portion M which is disposed tachable hatch or canopy arrangements for'airin longitudina y Spaced relation with respect craft crew cockpits or cabins which are arranged to the wind screen 12. The space between to be artificially pressurized for the benefit of the wind screen I! and the canopy I4 is arranged occupants when flying at high altitudes. One of to be enclosed y means Of a hateh which s the objects of the invention is to provide an ndi a d e e y at r normal pa se improved hatch or canopy arrangement for the entrance and exit purposes the hatch I5 is arpurpose referred to which incorporates novel fearanged to Slide longitudinally of the e e 0 tures whereby the canopy and associated fuselage as to telescope over the fixed canopy portion I so structures are of suitable rigidity to withstand as to uncover the, space between the wind screen the encountered pressure differential and whereand the canopy emergeney t P by the hatch is adapted to be quickly released poses the hatch l5 5 arranged to be comp y from connection to the fixed fuselage structure and quickly detached from the fusela 50 s o for emergency exit purposes in improved manner. 15 fly 016a! therefrom in p e o e rces of Another object is to provide an improved air-' gravity i the e t v airstream. craft cockpit enclosure arrangement comprising T0 Provlde the hatch to mounted p cooperative permanent and impermane t 1 the fuselage ill for the sliding movement referred m t which are adapted t normany provide to in connection with normal entrance and exit of an atmospherically sealed structure which is the Passengers. the hatch carries t s oppo ite adapted to be adjusted to passenger entrance lower side edge portions a plurality of longitudiand exit conditions in improved manner. More, e y spaced roller devices. Asillustrated by Figs.

specifically an object f t invention is to 2 and 3, the hatch is fitted adjacent each lower vi an improved Sliding hatch and ft r deck side edge thereof with a longitudinally extending arrangement for aircraft of types wherein the 26 bracket 20 upon which are mounted spaced pins fuselage plan forms thereof are substantially 22 each Carrying a p of ers Atrackparallel sided, whereby the after deck arrangey comprising a double channel haped bracket ment is adapted to be automatically adjusted be- 26 15 mounted upon a d f h fixed fuselage tween normal and collapsed positions in improved structure $0.35 to extend in registry with each manner in connection with cockpit covering and system of 1 ik d, 01 t s purp se the uncovering movements of the hatch. Other obtrack brackets e arranged to rest up jects and advantages of the invention will appea corresponding P e e ding rigidly from the specification hereinafter. from h se eaqute i wall structure 29. In t drawings; Pairs of hooks0 -3ll are carried by the fixed fuse- Fig. 1 is a fragmentary side elevation of an 5;1?' l Ch -T a be e plained in detail herealrplane cockpit enclosure arrangement of the i i a d no a y ext nd into hookin eninventlon, with portions broken away to sh0w,- Lg WPBFQY it slde e p rtions of actuating mechanism therefor; 4 e-3 P @a e t0 fi m y cl mp the Fig. 2 is a fragmentary section, on an enlarged 1'?' l i?l plates -4 scale, taken along the line II-II of Fig. 1; n 2 9 1 32 a ed to extend Fig. 3 is a fragmentary section, on an enlarged rigidly from the "11.591388 fixed Structure at each scale, taken along line III-III of Fig. 1; side thereof as to lie parallel to each of the brack- Fig. 4 is an enlarged detail of a fragment of the i and an atmosphere Sealing gasket D01"- canopy release mechanism; non 15 held by a corresponding b ac et 35 to Fig 5 a fr t y plan of a Damon of the extend from each of the plate 32-42 into presoperating mechanism thereof; i sure sealing engagement against the correspond- Fig. 6 is a fragmentary section taken along lines mg hatch bracket v .v1 of Fig 5; and Other gasket portions 35-46 are arranged pe- 1 7 is a t i of at sealing device ripherally ofthe'front and rear ends, respectively,

thereof, of the hatch 15 to engage in pressure sealing re- The drawings illustrate the invention in conlation against contiguous portions of the wind junction with an aircraft having a crew cockpit screen l2 and the fuselage canopy .or rear deck enclosed in a fuselage or nacelle portion indicated it to complete the pressure sealing of the cockpit ra y at The cockpit is enclosed at its when the hatch is in closed position (Figs. 1 and J forward end by means of awind screen l2, and at 5). A suitable air compression mechanism and control valve arrangement is provided in conjunction with the interior of the continuous gasket unit 34-35-36, such as a nipple 31 and a control valve 36, whereby upon closing of the hatch l5 9. supply of air under pressure may be admitted to the interior of the gasket unit so as to swell the latter into pressure sealing condition between the hatch and fixed fuselage structures. Prior to cockpit uncovering movement of the hatch, the air within the gasket unit may he released, and thus it will be understood that the hatch will be free to be rolled rearwardly upon the tracks 26-26 to uncover the cockpit for normal entrance and exit of the aircraft occupants, and that in connection with such movement the hatch will simply slide relative to the retracted gasket devices without damage thereto. I Preferably, the control lever 36 of the air control valve 38 will be operably associated with the hatch actuating mechanism, as will be referred to hereinafter, whereby the air pressure within the gasket will be automatically released at the commencement of each hatch uncovering movement and whereby air under pressure will be automatically delivered into the gasket upon completion of each cockpit closing movement of the hatch.

To actuate the hatch l5 between open and closed positions from interiorl of the cockpit, the brackets 20-20 are formed with longitudinally toothed rack portions 40-40 arranged in geared relation with corresponding spur gears 42-42 which are rotatably carried upon the fixed fuselage structure by means of pins 44-44. Corresponding drive gears 46-46 are meshed with the gears -42, and are keyed to a common shaft 41 which is arranged to be rotated through means of a sprocket-chain arrangement which is indicated generally at 48 as being manually operable 'by a crank handle 50 (Fig. 3). Thus, it will be understood that rotation of the crank handle 50 in opposite directions will provide corresponding backward and forward rolling movements of the hatch l5.

To permit the hatch l5 to be completely detached from the aircraft and to be blown clear thereof while the aircraft is in flight for emergency exit purposes, the hooks 30-30 which normally clamp the track brackets 26-26 to the fixed fuselage structure are arranged to be quickly swung out of clamping position in response to manual manipulation of a control device which is operable from interiorly of the cockpit. To this end the hooks 30-30 are each pivoted to the fuselage structure as at 52 (Figs. 2 and 4) and are pivotally connected at their lower ends by means 01' connections 54-54 to corresponding links 56-56 which screw threaded engage within sockets 51 extending into paired common pivotal connections at 58 with a clevis 58 which extends downwardly into pivotal connection with crank arm portion 60 of a control rod 62. The control rods 62 of each pair of hooks 30-30 are interconnected by means of a push pull member 64 which engages lugs 65 of the control rods; and the push pull members 64-64 at opposite sides of the hatch connect at one end of the cockpit to a common control shaft 61 having an actuating handle 66. Thus, it will be understood that simple manipulation of the control handle 68 will result in prompt disengagement of all of the clamps 30 whereby the track brackets 26-26 will be freed from the fixed fuselage structure and the entire hatch assembly detached from the aircraft. Hence, if the aircraft is flying in inverfed attitude when the hooks 30 are disengaged the hatch will simply fall away from the cockpit; or if the aircraft is flying away from the cockpit so as to quickly and completely uncover the cockplilt so that the occupants may escape by parac ute.

The track brackets 26-26 abut at their rear ends with corresponding similar track extension members 69-69 (Fig, 1) which are permanently fixed to the main fuselage structure so as to accommodate normal rearward rolling movement 01' the hatch l5. However, the junctures between the forward and rearward track portions 26-69 are inclined as shown so that the forward sections 26-26 overlie the rear sections 66-66 to avoid possible interferences with emergency detachment movements of the track brackets 26- 26, as explained hereinabove.

In connection with modern airplane design practice the fuselage may with facility be given a substantial curvature along its upper side view profile whereby the rear deck portion as at M of the aircraft of the drawings may be given a substantial slop downwardly away from the top elevation of the juncture with the sliding hatch. Hence, the hatch rails 26-26 may be disposed parallel to the fuselage center line so that movements thereof are not interfered with by gravity forces, and as the hatch slides rearwardly over the canopy M the hatch end structure and gasket portion 36 naturally move clear of the top surface of the canopy. However, in view of certain prime considerations with respect to the power plant and personnel space arrangements it is presently common practiceto shape the fuselage of a modern aircraft so as to be substantially straight line in plan form at the mid section thereof. Consequently, the side wall portions of the rear deck as at l4 in the drawings, cannot with facility be shaped to recede inwardly to any substantial degree just aft of the sliding hatch section. Therefore, it is arranged in the case of the present invention that portions of the side wall structures of the fixed canopy or rear deck 44 will be automatically retracted inwardly in con- Junction with each rearward rolling movement of the hatch l5; and the mechanism for so retracting the rear deck side wall portions is controlled by a cam mechanism which operates'upon rolling movement of the hatch to alternately contract and expand the deck structure as required for the purpose referred to. Hence, the movable hatch l5 may be rolled rearwardly from cockpit closing position to telescope over the rear deck portion l4 of the fuselage for normal entranceexit purposes without interference by the fixed fuselage parts with sliding movement of the hatch.

To this end the hatch I5 is formed at its rear end (Figs. 5 and 6) with a pair of cam plates 10 at each side thereof for camming engagement with a corresponding roller 12 carried by a bell crank 14 which is pivotally mounted upon the fixed fuselage structure by means of a pin 16. The roller 12 is arranged to bear against a camming edge portion 16 of the cam plate 10, and the cam edge 16 is formed with a well portion 18 which allows the roller to move thereinto in response to the action of a coil spring whenever the hatch is in cockpit closing position. The bell crank 14 pivotally connects at its opposite end through means of a swivel connector 82 with a push-pull member 84 which extends laterally therefrom into pivotal connection at 36 to one end of a bell crank 81 which is pivotally mounted by means of a bracket 88 to a pressure tight panel is formed to normally lie against the fixed" canopy structure so as to lap firmly thereagainst peripherally of the panel I00. Suitable weather sealing gasket devices are carried by the panel I for compressioned engagement with the fixed deck structure when in panel-closed position so as to weather seal the structure under normal conditions against ingress of dirt and rain water and ice and the like. A crank portionl04 extends from the arm 9.0 to carry a transverse Din I06 for engagement with the link 94 so as to provide a knuckle type Joint therebetween, whereby it will be understood that the linkage system comprising the members 9094 extending between the pivot connections 89-95 will be limited to unidirectional folding movement and that the dead center normal position thereof will render the system irreversible. That is, the link system will be inoperable to permit retraction of the sides of the canopy in response to air loads acting against the panels I00 from exteriorly thereof, but that the panels I00 will always be free to hinge in response to operation ofthe cam mechanism.

The bell crank 14 includes a third arm I01 which pivotally connects at I08 to a push-pull member I09 extending toward the rear end of the panel I00 into a position of pivotal engagement IIO (Fig. with one arm of a. bell crank II2 which pivotally mounts at I I4 upon a bracket II5 carried by the fixed fuselage structure. The other arm II6 of the bell crank connects by means of a swivel connection IIB to a link I extending into pivotal connection at I22 with one arm of a bell crank I24 which corresponds to the bell crank 81 hereinabove referred to. The other arm I25 of the bell crank I24 couples to a link I26 which corresponds to the link 94 hereinabove described through means of a knuckle joint connection I28; and the link I26 pivotally connects at I28 through a bracket I29 to a rear end portion of the panel I00.

Thus, it will be understood that camming movement of the roller I2 into the recess portion I8 of the cam plate 10 will force the knuckle joint links 94-I26 to move the panel I00 outwardly upon its hinge connection into weather sealing relation at its edges against the adjacent fuselage canopy structure. Due to the shape of the cam edge I6 of the plate I0, however, rearward I claim:

1. In an aircraft, a crew cockpit, a fixed canopy partially enclosing said cockpit, a hatch normally enclosing another portion of said cockpit and movable to telescope over said fixed canopy, said fixed canopy having its opposite side wall portions hingeable to contract inwardly, and cam means carried by said hatch and connected to said canopy side wall portions for automatically actuating the latter inwardly in conjunction with telescoping movements of said hatch.

2. In an aircraft, a crew cockpit, a fixed shell structure contiguous to said cockpit, a hatch normally enclosing said cockpit and movableto telescope over said fixed structure, said fixed structure having its opposite side wall portions hingeable to contract inwardly, and cam means carried by said hatch and connected to said fixed structure side wall portions for automatically actuating the latter inwardly in conjunction with telescoping movements of said hatch.

3. In an aircraft, a crew cockpit, a fixed canopy partially enclosing said cockpit, a hatch normally enclosing another portion of said cockpit and movable t'o telescope over said fixed canopy, said fixed canopy having its opposite side wall portions hingeable to contract inwardly, and cam means carried by said hatch and connected to said canopy side wall portions for automatically actuating the latter inwardly in conjunction with telescoping movements of said hatch and outwardly in conjunction with cockpit covering movement of said hatch.

4. In an alrcraft,,a crew cockpit, a hatch normally enclosing said cockpit, track means extending longitudinally of said hatch and engaging opposite side edge portions thereof for iongitudinal movement of said hatch relative to said track means, hook means carried by said aircraft to normally hook upon said track means to clamp the latter stationariiy relative to said aircraft, and manually operable control means connected to said hook means for unhooking the latter to release said hatch and track unit from said aircraft.

5. In an aircraft, a crew cockpit, a fixed structure rearwardly of said cockpit, a hatch normally enclosing said cockpit and movable horizontally to telescope over said fixed structure, said fixed /structure having its opposite side wall portions rolling movement of the hatch I5 will automatically cam the roller 92 inwardly to thereby'actuate the bell crank and linkage mechanism to retract the panel I00 inwardly upon its hinge I02 so as to make room for the rearward rolling movement of the hatch I5, as explained hereinabove.

Although only one form of the invention has been illustrated and described in detail, it will be apparent to those skilled in the art that the invention is not so limited but that various changes may be made therein without departing from the spirit of the invention or the scope of the appended claims.

hingeable to contract inwardly, and cam means carried by said hatch and connected to said fixed structure side wall portions for automatically actuating the latter inwardly in conjunction with telescoping movements of said hatch and outwardly in conjunction with cockpit closing movements of said hatch.

6. In an aircraft, a crew cockpit, a hatch normally enclosing said cockpit, track means extending longitudinally of said hatch and engaging opposite side edge portions thereof for longitudinal movement of said hatch relative to said track means, hook means carried by said aircraftto normally hook upon said track means to clamp the latter stationarily relative to said aircraft, and manually operable control means connected to said hook means for unhooking the latter to release said hatch and track unit from said aircraft, and extension track members fixed to said aircraft to extend in continuation of said track means but freed from said track means whereby said hatch and track unit may move clear of said aircraft without interference from said extension track members.

7. In an aircraft, a crew cockpit, a hatch norj ried by saidaircraltito normally hook upon said track means'toclamp the'latter stationarily relativeto said aircraft, and manually operable control. means connected to said hook means for unhooking" the latter'to release said ha h and track unit from said aircraft; f

8. In an aircraft, -a crew cockpit, aliatch normally enclosing said cockpit, track means extending longitudinally ofsaid hatch and engaging opposite side edge portions thereof for longitudinal movement of said hatch relative to said track means, hook means carried by said aircraft to normally hook upon said track means to clamp the latter stationarily relative to said aircraft, manually operable control means connected to said hook means for unhooking the latter to release said hatch and track unit from said aircraft, and inflatable gasket means carried by said aircraft to extend toward said hatch and adapted to avoid interference with said longitudinal movement thereof when defiated and to be infiated to extend into pressure sealing contact relation with said hatch.

' 9. In an aircraft, a fuselage having a crew cockpit, a fixed compartment structure contiguous to said cockpit, a hatch normally enclosing-said ioockpit and movable to telescope over said fixed structure, gasket means carried by said fuselage and said fixed structure to contact said hatch in pressure sealing relation, said fixed structure having its opposite side wall portions hingeable to contract inwardly, and cam means carried by I said vhatch and connected to said fixed structure side wall portions for automatically actuating the latter inwardly in conjunction with telescoping movements of said hatch.

10. In an aircraft. a fuselage having a crew cockpit, a fixed structure contiguous to said cockpit, a hatch normally enclosing said cockpit and movable to telescope over said fixed structure, inflatable gasket means carried by said fuselage and said fixed structure to contact said hatch in pressure sealing relation and defiatable to disengage said hatch from said fuselage and said fixed structure, said fixed structure having its opposite side wall portions hingeable to contract inwardly, and cam means carried by said hatch and connected to said fixed structure side wall portions for automatically actuating the latter inwardly in conjunction with telescoping movements of said hatch.

11. In an aircraft, a crew cockpit, a fixed shell structure contiguous to said cockpit, ahatch normally enclosing said cockpit and movable to telescope over said fixed structure, said fixed structure having its opposite side wall portions hingeable to contract inwardly, cam means carried by said hatch, toggle link means connected to said fixed structure side wall portions and engageable by said cam means for automatically actuating the latter inwardly in conjunction with telescoping movements of said hatch.

12, .In an aircraft, a crew cockpit, a hatch nor- I mally enclosing said cockpit, track means extending longitudinally of said hatch and engaging opposite side edge portions thereof for longitudinal move ent of said hatch relative to said track means, a plurality of spaced hook means carried by said aircraft longitudinally thereof to normally hook upon said track means to clamp the latter stationarily relative to said aircraft, and control means connected to said hook means fOr unhooking the latter simultaneously to release said hatch and track unit from said aircraft.

HERBERT L. BOWERS. 

